Abstract: Traditionally, during ignition of a gas turbine engine, the fuel control valves are controlled to be nearly closed, in order to provide the small amount of fuel that is necessary to ignite the gas turbine engine. The error that is inherent in providing fuel flow through small openings results in a higher likelihood of start-up failures. Accordingly, a lightoff fuel pressure reduction system is disclosed that uses a pressure reducing regulator on a bypass flow path to temporarily reduce the pressure of fuel supplied to the fuel control valves. In this case, the fuel control valves may be maintained in a more open position during the ignition phase, which reduces the likelihood of ignition failures.

Abstract: Traditionally, integrated motor compressors utilize a radial penetrator that is connected to the motor stator via terminals and wires. This radial connection requires the motor stator to be installed within the compressor housing prior to the connection. In addition, the wires are subject to failure from rapid gas decompression. Accordingly, an axial penetrator is disclosed to provide a conductive path, through the housing, parallel to the longitudinal axis of an integrated motor machine (e.g., integrated motor compressor). This enables the connection to be performed prior to installation of the motor stator within the housing. This also enables the conductive path between the motor windings and axial penetrator to be formed, as a single integrated path, using the same conductive and insulative materials. In turn, this ensures that the entire conductive path behaves the same during decompression, reduces costs, simplifies the installation process, and increases the robustness of the connection.

Abstract: An integrated compressor comprises an electric motor that is prone to high temperatures. In a first cooling feature, axial and/or radial cooling channels are provided through the stator of the motor to supply coolant to portions of the stator that are prone to high temperatures. In a second cooling feature, jets are used to spray coolant towards the end-windings of the motor, to thereby cool the end-windings.

Abstract: An integrated compressor comprises an electric motor that is prone to windage losses, radial loads, and recirculation flows. According to a first feature, partial grooves or riblets may be formed on the surface of a motor stator that defines the radially outward boundary of the air gap between the motor stator and the motor rotor. These partial grooves or riblets may maintain low to moderate windage losses, while reducing radial loads in the motor. According to a second feature, a support structure may be designed with a nose portion that is configured to disrupt or otherwise reduce recirculation flows within the end-winding cavity housing the end-winding of the motor. According to a third feature, the spiral orientation of the top coil of the end-winding may be aligned with the rotation direction of the motor rotor to reduce recirculation flows within the end-winding cavity.

Abstract: In a traditional bearing cap, the temperature of the oil-wetted surface that defines the oil sump may experience high temperatures, which can result in oil degradation, oil varnish, and coking. Accordingly, a bearing cap is disclosed that reduces the temperatures experienced by the oil-wetted surface. In particular, the bearing cap may comprise one or more air insulation cavities, between the surface that is exposed to heated air and the oil-wetted surface that defines the oil sump, to provide a thermal barrier between the two surfaces.

Abstract: Even if the fuel pressure to a torch for igniting an air-fuel mixture in a gas turbine engine is set to an ideal value, the actual fuel pressure supplied to the torch may differ due to modifications, drift, changes in ambient temperature or pressure, fuel composition, and/or the like. This may result in failure of the gas turbine engine to ignite. Accordingly, disclosed embodiments introduce a torch active pressure control (TAPC) system into the flow path of fuel to the torch. The TAPC system is controlled to modulate the fuel pressure of the fuel supplied to the torch, according to a modulation profile. The modulation profile may traverse a range of fuel pressures in each of one or a plurality of sinusoidal, V-shaped, stepped, or other-shaped cycles, to increase the probability that the ideal fuel pressure, and therefore, flame height, is achieved, thereby increasing the likelihood of a successful lightoff.

Abstract: A turbomachinery power generation station can be too large and heavy for transportation. Thus, embodiments are disclosed for separating a full power generation station into road-ready turbine and generator trailers, as well as realigning and recoupling the trailers for operation of the power generation station at a desired destination.

Abstract: A system for injecting dry gases into one or more gas compressors includes a nitrogen gas supply system to generate a stream of conditioned nitrogen gas, a process gas supply system to generate a stream of conditioned process gas, and a compression device. The compression device is configured to receive and pressurize the stream of conditioned nitrogen gas or the stream of conditioned process gas, and direct a pressurized stream of conditioned nitrogen gas or a pressurized stream of conditioned process gas towards the one or more gas compressors. The system includes a first valve that provides selective fluid communication between the nitrogen gas supply system and the compression device to direct the stream of conditioned nitrogen gas towards the compression device or selective fluid communication between the process gas supply system and the compression device to direct the stream of conditioned process gas towards the compression device.

Abstract: A pneumatically variable nozzle vane is disclosed that is capable of performing the same or similar function as a mechanically variable nozzle vane. Within its core, each pneumatically variable nozzle vane may comprise one or more cavities in fluid communication with one or more outlets to eject a gas from the nozzle vane into a flow path of working fluid through the nozzle. Each cavity may be shaped to match an internal pressure gradient to the external pressure gradient of the nozzle vane. The gas may be ejected as a curtain, substantially perpendicular to the flow path through the nozzle, to thereby manipulate the flow of a working fluid through the nozzle in a similar manner as a mechanically variable nozzle vane. In an embodiment, each nozzle vane may have two cavities supplying outlets on both the pressure-side and suction-side of the nozzle vane.

Abstract: A system for coupling a first duct to a second duct configured for a gas flow with a gas turbine engine is disclosed. The system includes a first closed member and a second closed member. The first closed member is fixedly coupled to the first duct and defines an engagement surface. The second closed member is fixedly coupled to the second duct and defines a mating surface complementary to the engagement surface. The coupling of the first duct to the second duct includes one of the engagement surface and the mating surface complementarily receiving the other of the engagement surface and the mating surface such that a labyrinth interface is defined therebetween. Also, the first duct is sealed with respect to the second duct at the labyrinth interface such that a seepage of some of the gas flow through the labyrinth interface is restricted.

Abstract: Conventionally, trim balancing for a power turbine has been performed at the equipment coupling. Disclosed embodiments comprise a hub that is installed on the shaft. This hub enables trim balancing to be performed on the shaft coupling, closer to the rotor, which is more effective. The disclosed hub also enables unbalance corrections to remain with the power turbine after uncoupling. In addition, the use of the hub improves efficiency and eliminates safety risks faced by personnel in the field during coupling of the power turbine to the equipment.

Abstract: A tip shroud, comprising a plurality of tip shoes encircling a rotor assembly, in a turbine may deform due to thermal gradients experienced during operation of the turbine. This can make it difficult to remove the tip shroud during disassembly of the turbine. In an embodiment, to facilitate consistent and reliable removal of the tip shroud during each disassembly of the turbine, one or more, including potentially all, of the tip shoes of a tip shroud may be provided with one or more radially protruding puller hooks. Each puller hook enables an axial force to be transferred by one or more tools to an axially inner surface of the puller hook, to thereby produce axial movement of the tip shoe out of the tip shroud.

Abstract: Conventionally, trim balancing for a power turbine has been performed at the equipment coupling. Disclosed embodiments comprise a hub that is installed on the shaft. This hub enables trim balancing to be performed on the shaft coupling, closer to the rotor, which is more effective. The disclosed hub also enables unbalance corrections to remain with the power turbine after uncoupling. In addition, the use of the hub improves efficiency and eliminates safety risks faced by personnel in the field during coupling of the power turbine to the equipment.

Abstract: A system for coupling a first duct to a second duct configured for a gas flow with a gas turbine engine is disclosed. The system includes a first closed member and a second closed member. The first closed member is fixedly coupled to the first duct and defines an engagement surface. The second closed member is fixedly coupled to the second duct and defines a mating surface complementary to the engagement surface. The coupling of the first duct to the second duct includes one of the engagement surface and the mating surface complementarily receiving the other of the engagement surface and the mating surface such that a labyrinth interface is defined therebetween. Also, the first duct is sealed with respect to the second duct at the labyrinth interface such that a seepage of some of the gas flow through the labyrinth interface is restricted.

Abstract: Fuel injection for hydrogen-gas fuels poses risks with regard to emissions, flashback, and flame-holding events in a gas turbine engine. Accordingly, embodiments of a fuel injection system are disclosed that uniformly mix gas and fuel, while stabilizing a flame and facilitating maintenance. The fuel injection system may comprise a plurality of micromixer panels, mounted in windows of a frame that are arranged circumferentially around a longitudinal axis of the gas turbine engine. Each micromixer panel may comprise a plurality of axial channels, arranged around a central pilot body that is fixed in a grommet. Two or more internal fuel feeds may supply fuel to distinct subsets of fuel jets within the outlets of the axial channels, such that the fuel injection system may be operated in multiple stages.

Abstract: Large industrial machines, such as gas turbine engines, typically have a control room or control panel, acting as a single local control point from which the machine is operated. However, this prevents technicians from controlling the machine at locations that are distant from the control point, as may be necessary during servicing or operation. Accordingly, a system is disclosed that enables a wireless human-machine interface to be used to control the machine, in addition to a local human-machine interface. The system may ensure that only a single human-machine interface is able to control the machine at any given time, as well as prevent unauthorized devices from controlling the machine.

Abstract: A scribing device for a component includes a holder and a first scribing assembly coupled to the holder. The first scribing assembly includes a first scribing tool including a first scribing tip configured to define a first annular scribe mark on a circumferential surface of the component, and a first biasing member configured to bias the first scribing tool towards the circumferential surface of the component. The scribing device further includes a second scribing assembly. The second scribing assembly includes a second scribing tool including a second scribing tip configured to define a second annular scribe mark on the circumferential surface of the component, and a second biasing member configured to bias the second scribing tool towards the circumferential surface of the component.

Abstract: Known micromixers for fuel injection (e.g., in a gas turbine engine) experience early burning or have limited operability. Accordingly, a micromixer is disclosed that utilizes an air nozzle, in combination with one or more fuel jets, to produce short flames that minimize the emission of nitrogen oxides, while providing additional benefits, such as mechanical robustness, aerodynamic efficiency, resistance to flame damage, suitability for additive manufacturing, wider operating ranges, operation with a variety of gaseous fuels, and/or amenability to control using conventional mechanisms.

Abstract: In a fuel injector, the temperature differential between a distributor plate, through which relatively cool fuel passes, and the manifold to which the distributor plate is bonded causes stresses and strains that can reduce the durability and longevity of the fuel injector. In disclosed embodiments, the distributor plate is bonded to an outer arm and inner arm. These arms act as levers to take up the stresses and strains caused by the temperature differential, thereby increasing the durability and longevity of the fuel injector.

Abstract: No known single-stage dry low emissions fuel injectors are capable of effectively operating over all ranges of hydrogen concentrations in hydrogen/natural gas fuel mixtures. Accordingly, a fuel injector is disclosed that is capable of operating in both a premix mode for fuel mixtures with lower hydrogen concentrations and a micromix mode for fuel mixtures with higher hydrogen concentrations. The fuel injector may comprise premix jets near an inlet of the fuel injector, optionally within one or more swirlers, and micromix jets near the outlet of the fuel injector. In the premix mode, fuel with lower hydrogen concentrations is provided to the premix jets, whereas in the micromix mode, fuel with higher hydrogen concentrations is provided to the micromix jets.